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Aircraft design initial_sizing_2
- 1. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Initial Sizing February 10, 2009 Initial Sizing
- 2. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 3. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 4. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Quick method based on configuration sketch and aspect ratio Crude estimation of Max. L/D. Approx. SFC, weight change during cruise and loiter. Weight fractions for takeoff, climb and landing are used from table. We/W0 is estimated from statistical equation. W0 is calculated iterating W0 = Wcrew +Wpayload 1− “ Wf W0 ” − “ We W0 ” Initial Sizing
- 5. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 6. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method . W0 = Wcrew +Wfixed payload +Wdropped payload +Wfuel +Wempty (1) W0 = Wcrew +Wfixed payload +Wdropped payload +Wfuel + We W0 W0 (2) Initial Sizing
- 7. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 8. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Initial Sizing
- 9. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 10. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Engine Start, Taxi and Takeoff A reasonable estimate is W1/W0= 0.97 to 0.99 Climbing and Accelerating to cruise alt. and Mach number M Subsonic: Wi /Wi−1 = 1.0065 - 0.0325 M Supersonic: Wi /Wi−1 = 0.991 - 0.007 M - 0.01 M2 Starting at Mach 0.1. For an acceleration beginning at other than Mach 0.1, the weight fraction calculated by the above equation for the given ending Mach number should be divided by the weight fraction calculated for the beginning Mach number. Initial Sizing
- 11. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Cruise Breguet Range Equation Jet : Wi Wi−1 = exp −RC V (L/D) (3) Prop : Wi Wi−1 = exp −RCbhp 550ηp (L/D) (4) During cruise and loiter - lift = weight L/D can be expressed as the inverse of the drag divided by the weight: L D = 1 qCd0 W /S + W S 1 qπAe (5) Wing loading value should be modified as per the situation. Initial Sizing
- 12. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Loiter weight fraction Jet : Wi Wi−1 = exp −EC L/D (6) Prop : Wi Wi−1 = exp −EVCbhp 550ηp (L/D) (7) where E is the endurance or loiter time. Descent for Landing – Historical value Wi /Wi−1 = 0.990 to 0.995 Landing and Taxi back – Historical value Wi /Wi−1 = 0.992 to 0.997 Initial Sizing
- 13. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 14. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method Initial Sizing
- 15. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 16. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing . Either the mission range or the performance must be considered a fallout parameter. W0 = NTper engine T/W (8) Range capability can be determined from Eqn.2 by considering the known takeoff weight as the guess W0 and varying the cruise legs to match the evaluated W0. Similar process may be taken for the other parameters. Initial Sizing
- 17. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 18. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 19. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Fuselage For certain types of aircraft, the fuselage size is determined strictly by “real-world constraints” – passenger aircraft. Initial Sizing
- 20. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Fuselage fineness ratio Ratio between the fuselage length and max. diameter. Theoretically, for a fixed internal volume subsonic drag is minimized by a fineness ratio of about 3 while supersonic drag is minimized by a fineness ratio of about 14. Wing Wing reference area (including the area extended to aircraft center line) is determined by Takeoff gross weight Takeoff wing loading Initial Sizing
- 21. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 22. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Definitions Initial Sizing
- 23. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Tail volume coefficient Vertical tail volume coefficient : cVT = LVT SVT bW SW (9) Horizontal tail volume coefficient : cHT = LHT SHT ¯CW SW (10) Initial Sizing
- 24. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Typical values for cHT and cVT Initial Sizing
- 25. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine Initial Sizing
- 26. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine 60% Initial Sizing
- 27. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine 60% Engines on the wing Initial Sizing
- 28. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine 60% Engines on the wing 50 – 55 % Initial Sizing
- 29. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine 60% Engines on the wing 50 – 55 % Aft-mounted engines Initial Sizing
- 30. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Moment arms LHT and LVT Engine positions Approx % of fuselage length Front mounted propeller engine 60% Engines on the wing 50 – 55 % Aft-mounted engines 45 – 50 % Initial Sizing
- 31. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Outline 1 Rubber Engine Sizing Review of sizing Refined Sizing Equation Empty-Weight Fraction Fuel Weight Summary of Refined Sizing Method 2 Fixed Engine Sizing 3 Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Initial Sizing
- 32. Rubber Engine Sizing Fixed Engine Sizing Geometry Sizing Fuselage and Wing Tail area Control Surface Sizing Control Surface Area Initial Sizing